KR20130062254A - Cooling system for gas turbine load coupling - Google Patents

Abstract

PURPOSE: An effective cooling system for a gas turbine rod coupling is provided to design and arrange air flow which is enough to remove heat to circulate a rod-coupling guard. CONSTITUTION: A gas turbine(33) comprises a rod coupling(35), a gas turbine package(31), a rod-coupling guard(65), and air channel rings for cooling(59,61,63). The rod coupling connects the gas turbine and a rod(37). The gas turbine package comprises a turbo machine compartment(55) which accommodates the gas turbine. The rod-coupling guard surrounds at least a part of the rod coupling. The air channel rings for cooling are designed and arranged to circulate the cooling air flow which is enough to remove heat from the rod coupling from a cooling air circulation system into the rod-coupling guard.

Description

Cooling system for gas turbine rod coupling {COOLING SYSTEM FOR GAS TURBINE LOAD COUPLING}

The present invention generally relates to gas turbines, in particular gas turbines, such as, but not limited to, aeroderivative gas turbines. More specifically, the present invention relates to the industrial application of aeronautical gas turbines for power generation, natural gas liquefaction or similar industrial applications.

Aerospace gas turbines are widely used in power generation for mechanical drive applications, as well as in power generation for industrial plants, pipelines, offshore platforms, LNG applications.

1 is a schematic diagram of a system having a gas turbine and a load mechanically driven by the gas turbine. More specifically, in the schematic diagram of FIG. 1, reference numeral 1 denotes a gas turbine for driving a rod 3, such as a compressor or compressor train, for a natural gas liquefaction line. The gas turbine 1 is connected to the rod 3 by a rod coupling 5. The rod coupling 5 comprises a shaft 7 and a joint 9. In the example of FIG. 1, the shaft 7 which is rotationally driven by the gas turbine 1 is connected to the gear box 11. The gear box 11 is connected to the rod 3 by an output shaft 13 of the gear box 11. The rod 3 may be provided on the same shaft with a number of rotating machines consisting of a single rotating machine or set, for example a compressor or a generator. An additional gear box can be arranged between two adjacent rotary machines driven by the turbine 1.

The gas turbine 1 includes a gas generator 15 and a power turbine 17. The gas generator 15 sequentially includes a compressor 19, a combustion chamber 21, and a high pressure turbine 23. The air entering the compressor 19 is compressed to high pressure and added to the combustion chamber 21 with liquid or gaseous fuel. The compressed hot combustion gas is first expanded in the high pressure turbine 23, which is connected to the compressor 19 via the inner shaft 25. Expansion of the combustion gas in the high pressure turbine 23 generates mechanical power, which drives the compressor 19 to rotate. The partially expanded combustion gas exiting the high pressure turbine 23 enters the power turbine 17 and is further expanded to generate mechanical power, which drives the rod 3 through the rod coupling 5. The exhaust combustion gas is collected by the collector-diffuser and discharged through the discharge line 27.

In the example shown in FIG. 1, the gas turbine is a single shaft gas turbine, ie a gas turbine in which a single inner shaft 25 connects the high pressure turbine 23 to the compressor 19 of the gas generator 15. The power turbine, sometimes also referred to as low pressure turbine, is supported by a shaft separate from the inner shaft 25 so that the gas generator 15 can rotate independently at a speed different from the power turbine 17. Other gas turbine embodiments provide different numbers of internal shafts and gas generators may include different numbers of compressors and turbines driving these compressors.

These turbines are typically aviation only turbines.

In the exemplary embodiment of FIG. 1, the rod 3 is connected to the so-called hot end of the gas turbine 1 via the rod coupling 5, ie to distinguish it from the cold end corresponding to the compressor 19 side. It is connected to the gas turbine side in which the power turbine 17 is arrange | positioned.

The rod coupling 5 undergoes temperature deformation due to the high temperature at the hot end of the gas turbine 1. The thermal deformation of the shaft 7 should be reduced, i.e. by means of the power turbine 17 or the rod bearings of the machinery arranged on the rod side, ie the gear box 11 (if present) and / or the gas turbine 1 Measures must be taken to prevent thermal expansion of the shaft 7 which damages the bearing of the driven rotary machine 3. Commonly taken measures include placing joints that can compensate for thermal expansion of the shaft. Nevertheless, the thermal expansion of the shaft generates axial forces on the bearings on both sides of the joint, ie on the turbine bearings and the gearbox or rotary machine bearings.

JP 2000-291446 A (Patent Document 1) discloses a gas turbine having a rod-coupled cooling system having a fan blade mounted on a rod coupling. The fan blades are rotationally driven by the rod coupling and generate a stream of cooling air from the surrounding environment through a guard surrounding the rod coupling. The use of fan blades driven by the rod coupling eliminates the need for additional compressors or fans to cool the rod coupling. However, blades can deform the kinematic behavior of the rod coupling, negatively affect its correct operation, and lead to dynamic stresses, vibrations and potential damage of the rotating parts and associated supports.

Japanese Unexamined Patent Publication No. 2000-291446

Thus, there is a need for more effective rod-coupling cooling systems.

As will be described below, with reference to some embodiments of the present invention, a particularly effective structure for delivering a stream of cooling air at least partially surrounding at least a portion of a rod coupling connecting a gas turbine and a rod is provided. Therefore, heat from the rod coupling is actively removed by forced air convection, thus reducing the thermal deformation of the rod connection and thereby reducing the axial load on the turbine and the rod bearing.

According to some embodiments of the invention, a gas turbine is provided, the gas turbine comprising at least a compressor; Power turbine; A rod coupling connecting the gas turbine to the rod; A rod-coupling guard at least partially surrounding the rod coupling; Cooling air channeling designed and arranged to circulate a cooling air flow into the rod-coupling guard sufficient to remove heat from the rod coupling. Forced air convection provided in the rod-coupling guard removes heat from the rod coupling and keeps the rod coupling at a low temperature, thus reducing the overall thermal strain of the rod coupling. As such, the axial load generated by thermal expansion of the rod bearing is also reduced when the gas turbine is connected to the rod at the hot end of the gas turbine, ie via the rod coupling at the power turbine side rather than at the compressor side.

More specifically, the present invention provides a gas turbine comprising a compressor, a power turbine, and a rod coupling connecting the gas turbine to the rod 37. A gas turbine package is also provided which consists of a turbomachine compartment containing a gas turbine. A rod-coupling guard is arranged around the rod coupling to at least partially surround the rod coupling. The cooling air circulation system is arranged and configured to circulate the cooling air to the turbomachine compartment. The cooling air circulation system delivers fresh ambient air into the turbomachine compartment to cool the turbomachine casing, ie the casing of the compressor and turbine (s) disposed therein. In addition, cooling air channeling for cooling the rod coupling is also provided. The cooling air channeling is designed and arranged to circulate the cooling air flow taken from the cooling air circulation system into the rod-coupling guard. Air flow circulated into the rod-coupling guard is sufficient to remove heat from the rod coupling and to remove its thermal and mechanical stresses. In some embodiments, the cooling air channeling is designed and configured to branch a portion of the ambient air discharged by the cooling air circulation system upstream of the turbomachine compartment, ie, before fresh ambient air enters the turbomachine compartment. . The air sent out to the rod-coupling guard by the cooling air channeling is thus almost at ambient temperature, so that a cooling improvement of the rod coupling is achieved.

A single air forced movement device can be arranged and designed to force the cooling air into the turbomachine compartment and through the cooling air channeling in the rod-coupling guard. Therefore, a simple structure with a limited number of auxiliary facilities is required to perform cooling of both the turbomachine casing and the rod coupling. The efficiency of the system is improved, and the overall reliability thereof is improved. More compact arrangements are also achieved. Since the cooling air flow around the rod coupling is generated by the same air forced movement device provided for turbomachine cooling, there may be no need for a separate air forced movement device to deliver cooling air to the rod coupling. . In addition, there is no need to mount a fan blade on the rod coupling as in the prior art described above.

In some embodiments, an air intake line or duct may be provided and arranged to be in fluid communication with the cooling air circulation system and the cooling air channeling. The air intake line may be provided with a filter device at its inlet. The filter arrangement filters both the ambient air required to cool the turbomachine casing as well as the ambient air required to cool the rod coupling. No separate filter device is needed. In some embodiments, the air intake line is in fluid communication with the air intake plenum, from which combustion air enters the compressor of the gas generator of the gas turbine. This further improves the efficiency of the system and reduces its cost since a single filter device filters the combustion air flow as well as the overall cooling air flow.

Further embodiments and advantageous features of the gas turbine according to the invention disclosed herein are described below.

In some preferred embodiments, the gas turbine is an aerospace gas turbine. The gas turbine may be a single-shaft gas turbine, ie a gas turbine in which the compressor is mechanically driven by a high pressure gas turbine and the compressor and the high pressure gas turbine are supported on a common shaft. The compressor and the high pressure gas turbine form a gas generator. The exhaust combustion gases exiting the high pressure turbine are further expanded in the power turbine. The power turbine is supported on an independent shaft and drives the rod in rotation. In some embodiments, a gear box is disposed between the power turbine and the rod.

In another embodiment, the gas turbine may be a dual- or three-shaft gas turbine comprising two or three compressors and two or three turbines, the coaxial shaft interconnecting the turbine and the shaft.

Regardless of the number of compressors and turbines and the number of coaxial shafts, a load coupling is provided between the power turbine, ie the turbine providing the power to drive the rod, and to drive the rod and the power turbine at different rotational speeds. May be interposed therefor. The rod coupling usually includes at least one shaft and one or more joints. The shaft may consist of one or more shaft sections or shaft portions that are interconnected.

In some embodiments, the rod coupling and rod-coupling guard extend through an exhaust gas plenum or exhaust collector-diffuser assembly that at least partially surrounds the rod coupling and rod-coupling guard. The exhaust collector-diffuser assembly is deployed around the axis of the gas turbine and collects and expands the exhaust expanded combustion gas into the environment, or delivers the expanded hot combustion gas, for example towards a steam turbine or other section of a cogeneration plant. .

In some embodiments, the gas turbine is at least partially disposed in a gas turbine package consisting of a turbomachine compartment containing the gas turbine. In some embodiments, an air circulation system is further provided for circulating cooling air to the turbomachine compartment. The rod compartment is preferably arranged downstream of the turbomachine compartment. The rod compartment is arranged on one side of the turbomachine compartment. Opposite air intake plenums are arranged on opposite sides of the turbomachine compartment so that air in the gas turbine compressor and air in the turbomachine compartment cools the exterior of the turbomachine casing. The rod coupling connecting the gas turbine and the rod preferably extends through the rod compartment. The rod-coupling guard may receive air from a cooling air circulation system or other dedicated source.

The cooling air channeling may comprise an air port, wherein cooling air from the cooling air circulation system is forcedly circulated. At least a first ventilation duct fluidly connects the air port to the rod-coupling guard, and in some embodiments, a second ventilation duct and, optionally, a third ventilation duct, to enable forced air circulation into the rod compartment. It is provided in fluid communication with the rod compartment.

The rod-coupling guard may end open at both ends, so that air forcedly circulated within the volume delimited by the rod-coupling guard may exit at both ends of the rod-coupling guard. This improves the cooling of the rod coupling even in parts extending out of the rod-coupling guard.

According to a further aspect, the subject matter disclosed herein relates to a method of reducing thermal and mechanical stress on a rod coupling in a gas turbine, the gas turbine comprising at least a compressor; Power turbine; And a rod coupling connecting the gas turbine to the rod. According to some embodiments, the method includes removing heat from the rod by forcibly moving cooling air around the rod coupling.

In some embodiments, a method is provided for reducing thermal and mechanical stresses on a rod coupling in a gas turbine. The method advantageously comprises the following steps: generating a cooling air stream to cool the casing of the gas turbine; Branching a portion of the cooling air stream upstream of a turbomachine compartment in which a gas turbine is disposed; And forcing the portion of the cooling air stream around a rod coupling connecting a gas turbine to the rod to remove heat from the rod coupling.

In some embodiments, the method includes forming a defined volume that at least partially surrounds the rod coupling; And forcibly circulating cooling air within the confined volume to remove heat from the rod coupling. It should be noted that heat is usually removed only from one part of the rod coupling, i.e. the closest to the hot end of the gas turbine, because thermal expansion is concentrated in this section of the rod coupling.

In an exemplary embodiment of the presently disclosed subject matter, the method includes disposing a rod-coupling guard at least partially surrounding the rod coupling, wherein the defined volume is at least partially by the rod-coupling guard. A step of defining; And removing heat from the rod coupling by forcibly circulating cooling air between the rod coupling and the rod-coupling guard.

In a further embodiment, the method may further comprise causing cooling air to escape from the defined volume at at least a first end of the rod-coupling guard facing the power turbine, thus the rod-couple At the first end of the ring guard a stream of cooling air exiting the confined volume is directed to the power turbine. In some embodiments, the method may further comprise causing cooling air to escape from the confined volume at at least a second end of the rod-coupling guard facing the power turbine, and thus the rod- A stream of cooling air exiting the defined volume at the second end of the coupling guard is directed from the power turbine to the rod. The second end of the rod-coupling guard may be open towards the environment, ie outside the turbine package.

According to some exemplary embodiments, the method includes arranging a gas turbine in a gas turbine package; Generating a cooling air stream to cool the casing of the gas turbine; Leaving a portion of the cooling air stream toward a defined volume that partially surrounds the rod coupling.

The gas turbine package usually further includes a rod compartment between the gas turbine and the rod. The rod coupling and the defined volume surrounding the rod coupling may be arranged at least partially in the rod compartment, and the cooling air may also be circulated in part and in part of the defined volume.

Features and embodiments are described below, which are further set forth in the claims, which form part of this specification. The above brief description illustrates the features of various embodiments of the present invention in order that the detailed description that follows may be better understood and in order that the contribution of the present invention to the art may be better understood. Of course, there are other features of the present invention which will be described below and set forth in the claims. In this regard, before describing the various embodiments of the present invention in detail, it should be understood that various embodiments of the present invention are not limited to the details of arrangement and structure of components shown in the following description or shown in the drawings in their application. do. The invention may be other embodiments and may be practiced and carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.

Thus, those skilled in the art will appreciate that the concepts underlying the present invention can be readily utilized as a basis for designing other structures, methods and / or systems for carrying out the various purposes of the present invention. Therefore, it is important that the claims be considered to include such equivalent constructions without departing from the spirit and scope of the invention.

A more complete understanding of the disclosed embodiments and their various attendant advantages will be readily apparent by reference to the following detailed description set forth in conjunction with the accompanying drawings.
1 shows a gas turbine and compressor structure according to the prior art.
2 is a diagram illustrating a gas turbine and compressor structure embodying the gist of the present invention.
3 is a schematic cross-sectional view along the vertical plane of the structure of FIG. 2.
4 is a cross-sectional view taken along the line IV-IV in Fig.
5 shows a further embodiment of a gas turbine and rod structure according to the invention.

DETAILED DESCRIPTION The following detailed description of the exemplary embodiments refers to the accompanying drawings. Like reference symbols in the various drawings indicate like elements. In addition, the drawings are not necessarily drawn to scale. In addition, the following detailed description does not limit the invention. Instead, the scope of the invention is defined by the claims.

Reference throughout this specification to “one embodiment” or “an embodiment” or “some embodiments” is provided that at least one embodiment of the invention discloses a particular feature, structure, or characteristic described in connection with the embodiment. It means to be included in. Thus, the appearances of the phrase “in one embodiment” or “in an embodiment” or “in some embodiments” in various places throughout the specification are not necessarily referring to the same embodiment (s). In addition, certain features, structures, or features may be combined in any suitable manner in one or more embodiments.

2 is a schematic diagram of a system embodying the gist of the present invention. The system includes a gas turbine and a rod connected to the gas turbine by rod coupling. More specifically in the schematic diagram of FIG. 2, a gas turbine package 31 comprising a gas turbine 33 is connected to the rod 37 by a rod coupling 35. In the exemplary embodiment shown in FIG. 2, the rod 37 is shown as a compressor, such as a compressor for a refrigerant in a natural gas liquefaction system. In the exemplary embodiment shown in FIG. 2, a gearbox 38 is arranged between the gas turbine and the compressor 37. The compressor 37 may be one of a series of compressors that form a compressor train driven by the same gas turbine 33. It should be appreciated that other types of rods may be driven by the gas turbine. For example, the rod may be a generator of a power plant. The rod coupling may have one or more gearboxes and / or a rotating machine such as one or more electrical or turbomachines.

In the exemplary embodiment shown in FIG. 2, the gas turbine package 31 has an air intake plenum 39 in fluid communication with the air intake line 41 and the inlet side of the compressor 43 of the gas turbine 33. Include. The gas turbine 33 may be composed of a high pressure turbine 45 and a power turbine 47. The high pressure turbine 45 is drive connected to the compressor 43 by an inner shaft (not shown). The combustion gas generated in the combustion chamber of the gas turbine is sequentially expanded in the high pressure turbine 45 to generate the power required to drive the compressor 43, and then in the power turbine 47 to drive the rod 37. Is swollen in For example, different gas turbine structures may be used that include two or more compressors sequentially and two or more turbines in series on the high temperature side of the gas turbine 33. In general, gas turbine 33 comprises a gas generator consisting of at least one compressor 43 and a high pressure turbine 45, the gas generator providing combustion gas at high temperature and high pressure, the combustion gas being one or more turbines. Inflate at 47.

In some embodiments the gas turbine 33 may be an aerospace gas turbine. The overall structure and arrangement, including multiple compressors, multiple turbines, multiple shafts, multiple compression and expansion stages for aeronautical gas turbines, may vary for each aerospace gas turbine. Suitable aviation gas turbines are the LM2500 + G4 LSPT or LM2500 aviation gas turbines, all available from GE Aviation in Evendale, Ohio, USA. Other suitable aviation gas turbines are, for example, PGT25 + G4 aviation gas turbines available from GE Oil and Gas, Florence, Italy, or Dresser- commercially available from Dresser-Rand Company of Houston, Texas, USA. Rand Vectra® 40G4 aviation gas turbine. In another embodiment, the aviation gas turbine may be a PGT16, PGT 20, or LM6000 aviation gas turbine available from GE Aviation, Evendale, Ohio, USA, all available from GE Oil and Gas, Florence, Italy. .

The combustion gases which expand and exhaust are collected in the exhaust diffuser-collector assembly 49 and are discharged towards the environment through the discharge line 51.

In the exemplary embodiment shown in the figure, the exhaust diffuser-collector assembly 49 is disposed in the rod compartment 53. The rod compartment 53 is arranged on the opposite side of the gas turbine package 31 with respect to the intake plenum 39, ie on the hot end side of the gas turbine. The rod coupling 35 extends from the power turbine 47 through the exhaust diffuser-collector assembly 49, which at least partially surrounds the rod coupling 35.

Some of the air sucked through the air intake plenum 39 at the cold end side of the gas turbine 33 flows through the gas turbine package 31, and more specifically, the middle portion of the gas turbine package 31. And flows through a turbomachine compartment 55 which at least partially receives the gas turbine 33. Air circulating in the turbomachine compartment 55 cools the casing of the turbomachine and is exhausted through the cooling air exhaust line 57.

In some embodiments, some of the cooling air sucked into the turbomachine compartment 55 exits the air duct 59 in fluid communication with the air port 61.

In the exemplary embodiment shown in the figure, the air ventilation duct 63 fluidly connects the air port 61 with the rod-coupling guard 65, the structure of which is best seen in FIG. 3. In some embodiments, the rod-coupling guard 65 consists of a cylindrical shell or sleeve 67 at least partially surrounding the shaft 69 forming part of the rod coupling 35.

In some embodiments, the rod-coupling guard 65 includes a first end 65A facing towards the gas turbine 33 and a second end 65B facing the rod 37. At least one such that cooling air forcedly circulated through the air port 61 and the ventilation duct 63 escapes from the limited volume or space defined by the cylindrical shell or sleeve 67 of the rod-coupling guard 65. The ends of and preferably both ends 65A, 65B can be opened, the volume of which is referred to at 70. In some embodiments, the first end 65A of the rod-coupling guard is oriented such that air exiting the first end 65A is forced to the exhaust diffuser-collector assembly 49. In some embodiments, the second end 65B of the rod-coupling guard 65 is such that a portion of the cooling air forced into the confined volume surrounding the rod coupling is discharged to the environment outside the turbine package. Can be open towards the environment.

In some embodiments, the air port 61 is further in fluid communication with the second ventilation duct 64, and in some cases also in fluid communication with the third ventilation duct 66 (see FIG. 4).

The second and third ventilation ducts 64, 66 include open ends disposed in the rod compartment 53, so that air forced into the ventilation ducts 64, 66 is discharged to the rod compartment 53. Air circulated to the rod compartment cools the rod compartment 53 and any device disposed therein.

According to this structure, the cooling air passing through the air duct 59 by the cooling air circulation system enters the first ventilation duct 63 as well as the second and / or third ventilation ducts 64 and 66. If present, they also enter these ventilation ducts. The air stream carried by the first ventilation duct 63 into the volume 70 surrounding the rod coupling 35 cools the rod coupling 35, more specifically the rod-coupling guard 65. Cool the shaft 69 surrounded by. The air flow exiting from both ends 65A, 65B of the rod-coupling guard 65 is not only from the shaft 69 portion extending from the rod-coupling guard 65, but also the rod-coupling guard 65. Forced to remove heat from the portion of one or more joints disposed on the shaft 69 from the outside. In addition, the air exiting from the open end 65A of the rod-coupling guard 65 is oriented towards the exhaust diffuser-collector assembly 49 and lowers the temperature in the region surrounding the rod coupling 35. To keep.

The temperature of the cooling air and the flow rate of the cooling air are, for example, the temperature of the rod coupling 35, more specifically the temperature of the shaft 69, not only on the turbine side, but also on the axial load on the shaft bearing on the rod side. It is advantageous to keep it at a value that significantly reduces it.

As can be seen in particular in FIG. 3, in some embodiments the open end 65A of the rod-coupling guard 65 is disposed within the hollow portion of the exhaust diffuser-collector assembly 49 through which the rod coupling 35 extends. do. As such, an effective cooling air stream exiting the tubular rod-coupling guard 65 is directed along the proximal end of the shaft 69 and in some cases the gas turbine ( Guided along a joint 69A disposed between the hot end of the 33 and the shaft 69, the heat rods caused by the hot exhaust gases are collected by the exhaust diffuser-collector assembly 49 and discharge line 51 To break away.

4 schematically shows a further joint 69B disposed on the rod coupling 35 in the region of the second open end 65B of the rod-coupling guard 65. Also in this region, the forced air stream exiting the open end 65B effectively cools this region of the rod coupling 35.

5 is a schematic view of a further embodiment of a gas turbine and rod structure according to the present invention. Like reference numerals are used to refer to parts, parts, or elements that are the same or similar to those described above in connection with FIG. 2.

The system comprises a gas turbine package 31 comprising a gas turbine 33 which is connected to the rod 37 by a rod coupling 35. In the example embodiment shown in FIG. 5, the rod 37 again comprises a compressor, for example a compressor for a refrigerant in a natural gas liquefaction system. The gearbox 38 may be disposed between the gas turbine and the compressor 37. In other embodiments, direct drive between the gas turbine and the rod may be provided, or other speed control device may be used instead of the gearbox. The compressor 37 may be one of a series of compressors that form a compressor train driven by the same gas turbine 33. It should be appreciated that other types of rods may be driven by the gas turbine. For example, the rod may be a generator of a power plant. The rod coupling may have one or more gearboxes and / or a rotating machine such as one or more electrical or turbomachines.

The gas turbine package 31 includes an air intake line or duct 41 and an air intake plenum 39 in fluid communication with the inlet side of the compressor 43 of the gas turbine 33. Also shown in FIG. 5 is a filter device 42 usually provided at the inlet of an air intake line or duct 41.

The gas turbine 33 may be composed of a high pressure turbine 45 and a power turbine 47. The high pressure turbine 45 is drive connected to the compressor 43 by an inner shaft (not shown). The combustion gases generated in the combustion chamber 44 of the gas turbine are sequentially expanded in the high pressure turbine 45 to generate the power required to drive the compressor 43, and then the power turbines to drive the rod 37. 47) is expanded within. For example, different gas turbine structures may be used that include two or more compressors sequentially and two or more turbines in series on the high temperature side of the gas turbine 33. In general, gas turbine 33 comprises a gas generator consisting of at least one compressor 43 and a high pressure turbine 45, the gas generator providing combustion gas at high temperature and high pressure, the combustion gas being one or more turbines. Inflate at 47. The power turbine (s) may be mechanically connected to the shaft of the high pressure turbine and the compressor. In an alternative embodiment, the power turbine 47 may be mechanically separated from the gas generator, ie the gas generator shaft and the power turbine shaft may be mechanically independent of each other.

The combustion gases which are expanded and exhausted are collected by the exhaust diffuser-collector assembly 49 and are discharged towards the environment through the discharge line or stack 51.

The exhaust diffuser-collector assembly 49 may be arranged in the rod compartment 53 which is disposed on the side opposite to the intake plenum 39, ie on the hot end side of the gas turbine 33. The rod coupling 35 extends from the power turbine 47 through the exhaust diffuser-collector assembly 49, which at least partially surrounds the rod coupling 35.

Combustion air is sucked by compressor 33 through an air intake line or duct 41 and filter arrangement 42 in suction plenum 39.

Through the same air intake line or duct 41 and filter device 42, fresh ambient air is also blown out towards the interior of the gas turbine package 31, more specifically through the turbomachine compartment 55 for cooling purposes. It is sent out. Fresh ambient air is also blown out of the air intake line or duct 41 toward the rod-coupled cooling device, as described in more detail below.

In some embodiments, a single fan, compressor, or any other air forced or air propulsion device, shown schematically at 46, is provided in the ventilation duct 48 in fluid communication with the air intake line 41. An air forced movement or air propulsion device is to be understood as any device suitable for delivering a sufficient air flow rate with sufficient air pressure for the purposes described below. The air sucked from the air intake line 41 by the fan 46 forms, through the duct 55A, the intermediate portion of the gas turbine package 31 and at least partly accommodates the gas turbine 33. Forced or propelled to 55. Air circulating to the turbomachine compartment 55 cools the casing of the turbomachine and is exhausted through an exhaust cooling air line 57.

In some embodiments, some of the cooling air sucked into the turbomachine compartment 55 exits the air duct 59 in fluid communication with the air port 61. In the exemplary embodiment shown in FIG. 5, the air ventilation duct 63 has an air port 61 with a rod-coupling guard 65 which may have the same structure as described above in connection with FIGS. 2 to 4. Connect fluidly. In some embodiments, the rod-coupling guard 65 consists of a cylindrical shell or sleeve 67 at least partially surrounding the shaft 69 forming part of the rod coupling 35.

In the embodiment of FIG. 5, the guard 65 also includes a first end 65A facing towards the gas turbine 33 and a second end 65B facing the rod 37. At least one end and preferably both ends 65A, 65B can be opened, so that the cooling air circulated through the air port 61 and the ventilation duct 63 is cylindrical in the rod-coupling guard 65. Escape from the limited volume or space 70 defined by the shell or sleeve 67. In some embodiments, the first end 65A of the rod-coupling guard is oriented such that air exiting the first end 65A is forced to the exhaust diffuser-collector assembly 49. In some embodiments, the second end 65B of the rod-coupling guard 65 is such that a portion of the cooling air forced into the confined volume surrounding the rod coupling is discharged to the environment outside the turbine package. Can be open towards the environment.

In some embodiments, the air port 61 is further in fluid communication with the second ventilation duct 64 and in some cases in fluid communication with an additional ventilation duct not shown. The ventilation duct (s) 64 are opened in the rod compartment 53, so that the air forced into the ventilation duct 64 is discharged to the rod compartment 53. The air circulated to the rod compartment cools the rod compartment 53, the surface of the exhaust collector-diffuser assembly 49, and any device disposed within the rod compartment 53.

In the embodiments of FIGS. 2-4 and 5 accordingly, therefore, the cooling air is to be directed not only through the gas turbine package and in particular the turbomachine compartment 55 but also into the rod-coupling guard surrounding the rod coupling. There is provided a single air source. A single fan, compressor or blower may be provided for forcing the cooling air to circulate not only around the turbomachine casing in the turbomachine compartment 55 but also around the rod coupling. Preferably, air is taken from the air intake line or duct 41.

In a preferred embodiment, the combustion air blown by the compressor 43 of the gas turbine 33 and circulated into the gas turbine package, in particular to the turbomachine compartment 55, to cool the turbomachine casing as well as around the rod coupling. A single filter arrangement 42 is provided for filtering both cooling air.

A compact device with reduced manufacturing and maintenance costs is obtained.

While embodiments of the subject matter described in this specification have been shown in the drawings and described in detail above in detail in connection with some exemplary embodiments, it is to be understood that the present teachings, principles and concepts of the invention are defined in the appended claims. It will be apparent to those skilled in the art that various modifications, variations and omissions may be made without departing from the advantages. Accordingly, the proper scope of the present invention should be limited only by the broadest interpretation of the claims to cover all such modifications, variations and omissions. In addition, the order or sequence of any process or method step may be changed or re-sequenced depending on the alternative.

31: gas turbine package 33: gas turbine
35: rod coupling 37: rod
38: gearbox 39: air intake plenum
41: air suction line 42: filter device
43: compressor 45: high pressure gas turbine
46: fan 47: power turbine
49: diffuser-collector assembly 51: discharge line
53: rod compartment 55: turbomachine compartment
59: air duct 61: air port
63: air ventilation duct 64: second ventilation duct
65: rod coupling guard 65A, 65B: end
66: third ventilation duct 67: cylindrical shell or sleeve
69: shaft 69A, 69B: joint

Claims (26)

In the gas turbine 33,
Compressor 43,
The power turbine 47,
A rod coupling 35 connecting the gas turbine 33 to a rod 37;
A gas turbine package 31 composed of a turbomachine compartment 55 for receiving the gas turbine 33;
A rod-coupling guard 65 at least partially surrounding the rod coupling 35;
A cooling air circulation system for circulating cooling air into the turbomachine compartment 55;
Cooling air channeling 59, 61, 63 designed and arranged to circulate a cooling air flow sufficient to remove heat from the rod coupling 35 from the cooling air circulation system into the rod-coupling guard. It characterized in that it comprises
Gas turbine. The method of claim 1,
And an air forced movement device 46 arranged and designed to force cooling air into the turbomachine compartment and through the cooling air channeling into the rod-coupling guard.
Gas turbine. 3. The method according to claim 1 or 2,
And an air intake line 41 in fluid communication with the cooling air circulation system and the cooling air channeling.
Gas turbine. The method of claim 3, wherein
The air intake line 41 is in fluid communication with an air intake plenum 39, wherein combustion air enters the compressor 43 from the air intake plenum.
Gas turbine. The method according to claim 3 or 4,
Further comprising a filter arrangement 42 arranged and configured to filter the ambient air entering the air intake line 41.
Gas turbine. 6. The method according to any one of claims 1 to 5,
The gas turbine is characterized in that the aircraft-only gas turbine
Gas turbine. 7. The method according to any one of claims 1 to 6,
The rod coupling 35 is connected to the hot end of the gas turbine
Gas turbine. The method of claim 7, wherein
The rod coupling 35 and the rod-coupling guard 65 extend through an exhaust collector-diffuser assembly 49 at least partially surrounding the rod coupling and the rod-coupling guard 65. Characterized by
Gas turbine. The method according to any one of claims 1 to 8,
Further comprising a rod compartment 53, wherein the rod coupling 35 extends through the rod compartment; The cooling air circulation channeling is arranged to deliver cooling air from the cooling air circulation system into the rod compartment 53.
Gas turbine. The method of claim 9,
The turbine package 31 comprises an air intake plenum 39 and the turbomachine compartment 55 is arranged between the air intake plenum 39 and the rod compartment 53.
Gas turbine. 11. The method according to claim 9 or 10,
The cooling air channeling comprises an air port (61), wherein cooling air from the cooling air circulation system is forced to circulate through the air port; At least a first ventilation duct 63 fluidly connects the air port 61 to the rod-coupling guard 65 and a second ventilation duct 64; 66 directs cooling air to the rod compartment 53. Characterized in that the transfer to
Gas turbine. The method of claim 11,
And a third ventilation duct (66; 64) for transferring cooling air into the rod compartment (53).
Gas turbine. 13. The method of claim 12,
The second ventilation duct 64 and the third ventilation duct 66 are disposed substantially symmetrically on both sides of the first ventilation duct 63.
Gas turbine. 14. The method according to any one of claims 1 to 13,
The rod-coupling guard 65 has a first end 65A facing the power turbine 47 and a second end 65B facing the rod 37 connected to the rod-coupling 35. At least the first end 65A is open, so that cooling air exiting from the rod-coupling guard 65 is directed towards the power turbine 47.
Gas turbine. 15. The method of claim 14,
The second end 65B is open, so that cooling air exiting from the rod-coupling guard 65 is directed towards the rod 37.
Gas turbine. The method according to claim 8 and 14 or 8 and 15,
The first end 65A of the rod-coupling guard 65 is disposed in a hollow space at least partially enclosed by the exhaust collector-diffuser assembly 49 and thus replaces the rod-coupling guard 65. The exiting cooling air cools the exhaust collector-diffuser assembly 49.
Gas turbine. 17. The method according to any one of claims 14 to 16,
The rod coupling 35 comprises at least a mechanical joint 69A; 69B and a shaft 69.
Gas turbine. 18. A system comprising a gas turbine 33 according to any one of claims 1 to 17 and a rod 37 driven by said gas turbine.
The rod 37 is characterized in that it is connected to the gas turbine by the rod-coupling 35.
system. A method of reducing thermal and mechanical stress on a rod coupling 35 in a gas turbine 33, wherein the gas turbine is disposed at least in the turbomachine compartment 55 of the gas turbine package 31. And a power turbine 47 and a rod coupling 35 connecting the gas turbine 33 to the rod 37, the method of thermal stress and mechanical stress reduction,
Generating a cooling air stream to cool the casing of the gas turbine 33;
Branching a portion of the cooling air stream upstream of the turbomachine compartment 55;
Forcing the portion of the cooling air stream around the rod coupling to remove heat from the rod coupling 35.
Thermal and mechanical stress reduction methods. The method of claim 19,
The forced air movement device is characterized in that for sending the cooling air through the turbomachine compartment 55 and around the rod coupling 35.
Thermal and mechanical stress reduction methods. 21. The method according to claim 19 or 20,
Forming a defined volume 67 at least partially surrounding the rod coupling 35;
Forcibly circulating said portion of a cooling air stream within said confined volume to remove heat from said rod coupling 35.
Thermal and mechanical stress reduction methods. 22. The method of claim 21,
Providing a rod-coupling guard 65 at least partially surrounding the rod coupling 35, wherein the confined volume 67 is at least partially defined by the rod-coupling guard 65. Providing the rod-coupling guard;
Further comprising removing heat from the rod coupling by forcibly circulating cooling air between the rod coupling 35 and the rod-coupling guard 65.
Thermal and mechanical stress reduction methods. 23. The method of claim 22,
Further comprising allowing cooling air to exit the confined volume 67 at least at the first end 65A of the rod-coupling guard 65 facing the power turbine 47, and thus the A stream of cooling air exiting the confined volume at the first end 65A of the rod-coupling guard 65 is directed to the power turbine 47.
Thermal and mechanical stress reduction methods. 24. The method according to claim 22 or 23,
Further comprising allowing cooling air to exit the confined volume 67 at least at the second end 65B of the rod-coupling guard 65 facing the rod 37; A stream of cooling air exiting the confined volume at the second end of the coupling guard 65 is directed from the power turbine 47 towards the rod 37
Thermal and mechanical stress reduction methods. 25. The method according to any one of claims 21 to 24,
Providing a rod compartment 53 between the gas turbine 33 and the rod 37, and defining the rod coupling 35 and the defined volume 67 surrounding the rod coupling 35. At least partially arranging in the rod compartment 53 and transferring the cooling air into the rod compartment 53 in part and in the defined volume.
Thermal and mechanical stress reduction methods. In the gas turbine 33,
Compressor 43,
The power turbine 47,
A rod coupling 35 connecting the gas turbine 33 to a rod 37;
A rod-coupling guard 65 at least partially surrounding the rod coupling 35;
Cooling air channeling (51, 61, 63) designed and arranged to circulate a cooling air flow into the rod-coupling guard sufficient to remove heat from the rod coupling (35);
A gas turbine package 31 composed of a turbomachine compartment 55 for receiving the gas turbine 33;
A cooling air circulation system for circulating cooling air into the turbomachine compartment 55;
A rod compartment 53,
The rod coupling 35 extends through the rod compartment 53;
The cooling air channeling comprises an air port 61, wherein cooling air from the cooling air circulation system is forcedly circulated, and at least a first ventilation duct 63 connects the air port 61 to the rod- Fluidly connected to the coupling guard 65, characterized in that the second ventilation duct (64; 66) delivers cooling air into the rod compartment (53).
Gas turbine.

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